US20090075023A1 - Method for producing thermal barrier coating and a thermal barrier coating - Google Patents

Method for producing thermal barrier coating and a thermal barrier coating Download PDF

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Publication number
US20090075023A1
US20090075023A1 US12/209,941 US20994108A US2009075023A1 US 20090075023 A1 US20090075023 A1 US 20090075023A1 US 20994108 A US20994108 A US 20994108A US 2009075023 A1 US2009075023 A1 US 2009075023A1
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Prior art keywords
oxides
thermal barrier
barrier coating
component part
comprised
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US12/209,941
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English (en)
Inventor
Thomas Cosack
Andreas Jakimov
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: COSACK, THOMAS, JAKIMOV, ANDREAS
Publication of US20090075023A1 publication Critical patent/US20090075023A1/en
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/54—Controlling or regulating the coating process
    • C23C14/542—Controlling the film thickness or evaporation rate
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/08—Oxides
    • C23C14/083—Oxides of refractory metals or yttrium
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/54—Controlling or regulating the coating process
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/313—Layer deposition by physical vapour deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2112—Aluminium oxides
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24174—Structurally defined web or sheet [e.g., overall dimension, etc.] including sheet or component perpendicular to plane of web or sheet

Definitions

  • the present invention relates to a method for producing a ceramic thermal barrier coating on a component part for use in compressor and turbine components by means of a vapor depositing method as well as a thermal barrier coating for component parts for use in compressor and turbine components, wherein the thermal barrier coating is normally comprised of a ceramic thermal barrier coating having a columnar structure and columns being oriented substantially perpendicular to a surface of the component part.
  • the invention also relates to a component part for use in compressor and turbine components comprised of a metal substrate and a thermal barrier coating applied at least partially to the metal substrate.
  • a ceramic thermal barrier coating on component parts are known from the prior art, in particular for use in compressor and turbine components.
  • a ceramic layer is applied to the component part using either a plasma spray method or by means of a physical vapor depositing method (PVD).
  • PVD physical vapor depositing method
  • Ceramic layers with columnar structures arise through the use of physical vapor depositing methods, in particular also electron beam vaporization (EB-PVD).
  • EB-PVD electron beam vaporization
  • the columns have a constant thickness over their lengths. Even the columnar substructure of the column is homogeneous.
  • the advantage of ceramic thermal barrier coatings produced in this manner over the thermal barrier coatings produced by a thermal spray process is that they have an improved resistance to thermal change due to the columnar structure.
  • the individual columns permit an expansion and contraction of the column structure without stress occurring, which in extreme cases could lead to individual parts of the thermal barrier coating flaking off.
  • the material temperature of the component part is reduced and strength is thereby maintained.
  • Zirconium oxide with various stabilizers, particularly yttrium oxide is used as the ceramic material most of the time in this case.
  • Methods for producing ceramic thermal barrier coatings and corresponding thermal barrier coatings for metal component parts for use in compressor and turbine components are known from German Patent Document Nos. DE 601 03 526 T2 and DE 693 18 856 T2 as well as from U.S. Pat. Nos. 4,321,311 A, 4,401,697 A, 4,405,659 A and 5,514,482.
  • the objective of the present invention is providing a generic thermal barrier coating for a component part with a very clearly reduced thermal conductivity.
  • another objective of the present invention is providing a component part for use in compressor and turbine components comprised of a metal substrate and a thermal barrier coating applied at least partially to the metal substrate, wherein the thermal barrier coating features a very clearly reduced thermal conductivity as compared with known thermal barrier coatings.
  • An inventive method for producing a ceramic thermal barrier coating on a component part for use in compressor and turbine components comprises a vapor depositing method with the following method steps: a) provision of a ceramic vapor for depositing on the component part; b) depositing of the ceramic vapor on the component part to form a thermal barrier coating having a columnar structure, the columns being oriented substantially perpendicular to a surface of the component part; and c) varying of at least one method parameter during method step b), in such a way that the resultant thermal barrier coating comprises columns, which have different geometries, in particular alternating decreasing and increasing diameters.
  • the ceramic vapor or the ceramic material is comprised of zircon oxide or zirconium oxide and A 2 O 3 , wherein the A in A 2 O 3 is selected from a group comprising Er, Nd, Yb, Eu, Dy, Gd, Sc, La, Al and Pr.
  • the ceramic vapor or the ceramic material be comprised of a zircon oxide or zirconium oxide and a mixture of at least two oxides from a group of oxides, which group is comprised of Er 2 O 3 , Nd 2 O 3 , Yb 2 O 3 , Eu 2 O 3 , Dy 2 O 3 , Gd 2 O 3 , Sc 2 O 3 , La 2 O 3 , Al 2 O 3 and Pr 2 O 3 or which group is comprised of oxides of Er, oxides of Nd, oxides of Yb, oxides of Eu, oxides of Dy, oxides of Gd, oxides of Sc, oxides of Al, oxides of La and oxides of Pr.
  • the vapor depositing method is particularly a physical vapor depositing method, such as, for example, an electron beam vapor depositing method.
  • a cathode sputtering method or an arc welding vaporization method as well as CVD methods is also conceivable.
  • the use of a vapor depositing method guarantees that the developing thermal barrier coating has a columnar structure and thus the already known advantages of such structured ceramic thermal barrier coatings are retained.
  • the emerging columns have different geometries, in particular alternating decreasing and increasing diameters. Because of the alternating decreasing and increasing diameters, pores develop between the individual columns in the course of the layer development of the thermal barrier coating and these pores contribute to clearly reducing the heat flow and thus the thermal conductivity of the emerging thermal barrier coating.
  • the feature of the decreasing and increasing diameters should also be understood in particular in this case such that adjacent columns do not touch at least in sections over their lengths and do not run parallel. The same applies to any substructure that may develop.
  • the smaller diameters of the individual columns advantageously massively inhibit the flow of heat so that this also results in a substantial reduction in the thermal conductivity of the emerging thermal barrier coating.
  • the method is carried out in a coating chamber, in particular a vacuum chamber.
  • the to-be-coated component part is introduced into the coating chamber and the ceramic thermal barrier coating is deposited on it.
  • the component part is normally warmed or heated at least on the to-be-coated surface of the component part.
  • oxygen and inert gas can be fed in during method step b) and the varying of at least one method parameter during method step c) to be comprised of varying the partial pressure of oxygen and/or of the inert gas during coating or in the coating chamber.
  • the partial pressures and even the overall pressure can be regulated via the gas flows or the pumping capacity.
  • the to-be-coated component part to be moved during method step b) and the varying of at least one method parameter during method step c) to be comprised of varying the type of component movement and/or component speed during coating.
  • the component part can be rotated in particular so that the varying of at least one method parameter during method step c) is comprised of varying the rotational speed during coating.
  • the varying of at least one method parameter during method step c) can be comprised of varying the deposition rate of the ceramic vapor on the component part during coating.
  • the thermal barrier coating is deposited in a thickness of between 1 and 400 ⁇ m, however, other layer thicknesses are also conceivable.
  • a bonding layer is formed at least partially between the to-be-coated component part surface and the thermal barrier coating.
  • the bonding layer in this case can be comprised of MCrAlY alitized/Al-enriched surfaces, or Pt/Al.
  • the bonding layer can be applied by means of known thermal spray methods, galvanic methods, diffusion treatment methods or even by means of physical vapor depositing methods.
  • an intermediate layer of aluminum oxide it is possible for an intermediate layer of aluminum oxide to be formed at least partially between the to-be-coated component part surface and the bonding layer.
  • An inventive thermal barrier coating is comprised of ceramic material and has a columnar structure or grain structure, wherein the columns are oriented substantially perpendicular to a surface of the component part. According to the invention, the columns have different geometries, in particular alternating decreasing and increasing diameters along their longitudinal extensions.
  • the ceramic material of the thermal barrier coating is comprised of zircon oxide or zirconium oxide and A 2 O 3 , wherein the A in A 2 O 3 is selected from a group comprising Er, Nd, Yb, Eu, Dy, Gd, Sc, La, Al and Pr.
  • the ceramic material of the thermal barrier coating be comprised of a zircon oxide or zirconium oxide and a mixture of at least two oxides from a group of oxides, which group is comprised of Er 2 O 3 , Nd 2 O 3 , Yb 2 O 3 , Eu 2 O 3 , Dy 2 O 3 , Gd 2 O 3 , Sc 2 O 3 , Al 2 O 3 , La 2 O 3 and Pr 2 O 3 or which group is comprised of oxides of Er, oxides of Nd, oxides of Yb, oxides of Eu, oxides of Dy, oxides of Gd, oxides of Sc, oxides of Al, oxides of La and oxides of Pr.
  • the grain boundaries of the individual columns can touch at least partially, advantageously forming pore spaces between the individual columns.
  • the preferred development of the inventive structure or formation of the individual columns results in a clear reduction in the thermal conductivity of the thermal barrier coating since the small diameters of the individual columns massively inhibit the flow of heat.
  • the pores formed within the thermal barrier coating significantly reduce the flow of heat.
  • the thermal barrier coating normally features a thickness of between 1 and 400 ⁇ m, wherein other thicknesses are also conceivable.
  • An inventive component part for use in compressor and turbine components is comprised of a metal substrate and an inventive thermal barrier coating applied at least partially to the metal substrate, as described in the foregoing.
  • a correspondingly coated component part has a clearly lower wear rate with a correspondingly higher service life due to the clear reduction of the thermal conductivity of the thermal barrier coating in accordance with the present invention.
  • a bonding layer in particular made of MCrAlY and Pt/Al, can be formed at least partially between the substrate and the thermal barrier coating. It is also possible for an intermediate layer made of aluminum oxide to be formed at least partially between the substrate and the bonding layer.
  • the inventive component part is an element of a gas turbine engine in particular.
  • FIG. 1 is a schematic sectional representation of a component part with a thermal barrier coating in accordance with the prior art
  • FIG. 2 is a exemplary, schematic sectional representation of a component part with an inventive thermal barrier coating
  • FIG. 3 is another exemplary, schematic sectional representation of a component part with an inventive thermal barrier coating.
  • FIG. 4 is a further exemplary, schematic sectional representation of a component part with an inventive thermal barrier coating.
  • FIG. 1 shows a schematic sectional representation of a component part or a metallic substrate 18 with a thermal barrier coating 22 arranged on it.
  • a bonding layer 20 in particular made of MCrAlY or Pt/Al, is formed between the thermal barrier coating 22 and the surface 16 of the component part.
  • the thermal barrier coating 22 has a columnar structure, wherein the individual columns 24 are oriented substantially perpendicular to the surface 16 of the component part.
  • the grain boundaries 26 , 28 of respectively different columns 24 touch in the process over the longitudinal extension of the column 24 . This results in a relatively thick columnar structure that promotes the flow of heat within the ceramic thermal barrier coating 22 .
  • FIGS. 2 through 4 each show a schematic sectional representation of a ceramic thermal barrier coating 10 , which was applied to component part surface 16 of the component part 18 or was deposited there; it must be noted that no reference numbers have been entered in FIGS. 3 and 4 , however, they are applicable there in a corresponding manner.
  • the thermal barrier coating 10 is again comprised of columns 12 , which are oriented substantially perpendicular to the surface 16 of the component part.
  • the columns 12 shown in FIG. 2 have alternating decreasing and increasing diameters d, D along their longitudinal extensions.
  • the grain boundaries 30 of the individual columns touch at least partially, but pores 14 are formed between the individual columns 12 .
  • the heat flow within the thermal barrier coating 10 is massively inhibited.
  • the density of the thermal barrier coating 10 is clearly reduced due to the pores 14 so that the flow of heat within the thermal barrier coating 10 is also hereby clearly reduced.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Inorganic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Physical Vapour Deposition (AREA)
US12/209,941 2007-09-13 2008-09-12 Method for producing thermal barrier coating and a thermal barrier coating Abandoned US20090075023A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007043791.0 2007-09-13
DE102007043791A DE102007043791A1 (de) 2007-09-13 2007-09-13 Verfahren zur Herstellung einer Wärmedämmschicht und Wärmedämmschicht

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9869183B2 (en) 2014-08-01 2018-01-16 United Technologies Corporation Thermal barrier coating inside cooling channels
RU2742862C2 (ru) * 2016-08-25 2021-02-11 Сафран Способ получения термобарьерной системы на металлической основе детали турбомашины
US11492974B2 (en) 2020-05-08 2022-11-08 Raytheon Technologies Corporation Thermal barrier coating with reduced edge crack initiation stress and high insulating factor

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10260141B2 (en) * 2013-10-09 2019-04-16 United Technologies Corporation Method of forming a thermal barrier coating with improved adhesion
ITMI20132125A1 (it) * 2013-12-18 2015-06-19 Edison Spa Metodo per la deposizione di film di ossidi misti su substrati di materiale composito
WO2016151357A1 (en) * 2015-03-20 2016-09-29 Edison S.P.A. Method for the deposition of films of mixed oxides on composite material substrates

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US4401697A (en) * 1980-01-07 1983-08-30 United Technologies Corporation Method for producing columnar grain ceramic thermal barrier coatings
US4405659A (en) * 1980-01-07 1983-09-20 United Technologies Corporation Method for producing columnar grain ceramic thermal barrier coatings
US5514482A (en) * 1984-04-25 1996-05-07 Alliedsignal Inc. Thermal barrier coating system for superalloy components
US5350599A (en) * 1992-10-27 1994-09-27 General Electric Company Erosion-resistant thermal barrier coating

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9869183B2 (en) 2014-08-01 2018-01-16 United Technologies Corporation Thermal barrier coating inside cooling channels
RU2742862C2 (ru) * 2016-08-25 2021-02-11 Сафран Способ получения термобарьерной системы на металлической основе детали турбомашины
US11492974B2 (en) 2020-05-08 2022-11-08 Raytheon Technologies Corporation Thermal barrier coating with reduced edge crack initiation stress and high insulating factor

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DE102007043791A1 (de) 2009-04-02
EP2036999A1 (de) 2009-03-18

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